Aircraft



E. B. CARNS.

AIRCRAFT.

APPucATlou FILED luNE 3. lala.

Patented May 18, 1920. l l 3 SHEETS-SHEET 1.

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w am /Mm v atta-www3 E. B. CARNS.

AIRCRAFT.

APPLICATIQH FILED JUNE 3,1918.

Patented May 18 a SHEETS-SHEET 2.

. guna/Mig@ E. B. CAHNS.

AIRCRAFT.

APPLICATION FILED JUN 3. i918.

Patented May 18, 1920.

3 SHEETS-SHEET 3'.

Clffor IMIS EDMUND IB. CARNS, OF DETROIT, MICHIGAN.

' AIRCRAFT.

S'pecioat'ion of Letters Patent. Patented May 18, 1920.

Application led J'une 3, 1918. Serial No..v 237,893.

y To all whom t may concern:

Be it4 known that I, EDMUND B. CARNS, a citizen of the United States ofAmerica,

` residing at Detroit, in the county of Wayne and State lof Michigan,have invented certain new and useful Improvements in Aircraft, of whichthe -following is a specificaf tion, reference being had therein to theaccompanying drawings.

The invention relates to the construction -of aircraft and has for itsprincipal object the obtaining of a standardized construction whichcombines the advantages ofv simplicity, strength, lightness, and ease inmanufacture and assembly. In its broader features the invention isapplicable to various f types of aircraft, but as herein specificallyshown and described is applied to the construction of heavier-than-airmachines, or aeroplanes.

In the present state of the art it is usual in `the construction ofaeroplanes to form many parts of the frame-work of wood. This has-theadvantage of the flexibility and shock-absorbing properties inherent inthe structure of wood, but it also has many disadvantages, particularlyin limitingquantity production of the machines. The substitution ofmetal for wood has been heretofore thought impractical on account of toogreat rigidity and inability to withstand shocks without permanentdeformation. I have, however, overcome these defet/Lts, and haveobtained a metallic construction which has greater flexibility' andresiliency than the standard constructions heretofore employed and whichhas the Iadditional advantages as above set forth.

One of the 4essential featuresof my invention is the forming of thekstructure in standard units which may be easily assembled and permit ofshipment knocked-down. Another feature -is the flexible connection ofthe units' and the-shock-absorbing means therebetween. the more specificconstruction of the various parts of the machine will be referredtohereinafter. ,N v

In the drawings:

Figure 1 is a plan view of a portion of an aeroplane embodying myinvention;

Fig. 2 is a sectional plan view showing a portion of one of the strutmembers;

Other features relating to .A

Figf' is a sectional planl View of a portion of one of the Wing members;r

-Figffl is a cross-section through the upper and lower planes, showingthe brace' connections therefor;

Fig. 5 is a perspective view of the sleeve l[fitting and connections forthe strut-meme'rs;

brace anchorage and coupling for the strut members; y v 1 Fig. 7 is across-section through the fuse- 8 is a sectional plan view of the wingtip;

of sealing betweemwing sections; l

Fig. 10 is a perspective view of a portion of one ofthe rib members; tig. 11 is a cross-section therethrough;

an I

Fig. l2 ais a diagrammatic -plan of the wing frame showing the flexiblebracing therefor. v

Aeroplanes embodying my invention have the usual main elements, such asthe fuselage, wings, landing-gear, control-mecha? nism, ete- Which ingeneral design may be of any approved type. They differ, however, fromconstructions heretofore designed in dispensing with vwooden -membersand the substitution of metallic members therefor.

\ K Wings.

The wings areV composed'l of a series of serctionslAA etc., which areformed independently and are assembled in alinement with eachother.comprises a series of Asheet-metal stampings B having 'flangedpedges andof a .contour producing the desired camber. These stampin s, which I'shall term ribsQ have alined, anged apertures C to permit the sleevingof the same over spar-membersfD, which latter are preferably formed ofmetallicftubing. The ribs are also centrally out away at E to decreasethe weight therelof, and are cross-cpnnected by sheet-metal strutmembers F to hold the same in parallelism.v Thus a light metallic frameis formed over which the linen or other facing material may be drawnl toimpart the. de-

Fig. 6 is a section showing the combined Fig. 9 is a section showing themanner vEach of these sections sired form thereto. The forward andrear.v

edge portions are maintained the proper form by fashioned sheet-metaledge members G, secured over` the ribs B and preferably perforated forgreater lightness. The fabric H has a coating H of suitable material'forweather-proofing the fabric and is secured, 1preferably by sewing, tothe edge flanges of the rib members B, which flanges are perforated forthe passage of the thread and are preferably also-covered with a tape Ito prevent lcutting of the thread. The whole constitutes a section ofthe wing having suicient strength and rigidity to sustain the maximumwind 1pressure thereon and being alsoof a weight-less or no greater thanthat of an equal section of wing of standard construction. A

The wing sections are connected to a wingframe comprising the tubularspar-members D, before described, and strut-membersl J -forcross-connecting the same. In biplane or multi-plane constructionsthese` crossstrut-members` are connected with vertical strut-members tolform the elements of the truss. Each strut-member J comprises the.sleeves or -tubes K forl slipping over the spars, the horizontalnipplesK projecting from said sleeves and forming couplings for the connectingtubes K2 and the vertical nipples K3 for coupling Wi-th'the verticalstrut tubes K. Thersleeves K andthe horizontal member K2 are inclosed ina housingv section similar inform to the wing sections A, being composedof a pair of correspondrib members B and' a fabric covering.

v'Ihe rib members are apertured to be mounted upon vsleeves K and thelatter have struck-out portions lK5 forming abutments f or said ribs. Aportion of the sleeve projects beyond the web of the rib but not beyoudthe marginal flange of the rib which is turned outward. Thus inassembling-the parts the strut-members J are arranged between/ winsections without making any break in t e continuity of the outersurfaces thereof. Y

For imparting strength to the Wing-frames diagonal brace members areprovided, but instead of connecting these -members to the spars they areconnected to' the strutmembers. As shown, the brace-members L, which arepreferably formed of stranded wire cable, are tied to the adjacent endsofv the nlpples on thesleeves K and the strut-` `members engage `thesame, this .tie performing the .double function of a curing meansbetween said members andan anchora the brace. As before stated, thesleeves" K are' slidable upon the tubular spar-members, but the strut at\the outer end-of each. wing L .has its movement limited and resilientlyrey sisted, Thus, as the brace-members L extend from strut to strut andfrom the outer tothe innerend ofthtwing", any movement upon the felt,holding the for due to the flexing of the spars will be taken l up bythe resilient member, while the intermediate struts are perinittedindependent f movement. This imparts flexibility to the entire frame andequalizesthe stresses thereon, preventing a dangerous -overstressing atany one point.

- The sections A A', etc., are'sleeve'd upon the spar-members Dintermediate the strutmembers J and are freely slidable upon said sparsto adjust themselves to any iexing of the' frame. To prevent impact uponthe truss members, cushions are arranged intermediate these members andthe wing sections, these preferably consisting of rings of felt orsimilar material sleeved upon the spars intermediate each section andthe adjacent strut. There isfalso preferably a felt bushing within eachsleeve K and felt washers between the nipples K and K3 on said bushingsand the struts in engagement therewith, so that metal-to-metal contactis avoided. This prevents the transmission of vibrations and absorbsshocks incident to the various stresses to which-the frame is subjected.As shown in detail in Fig. 2,

the sleeve K has placed thereon adjacent to the struckup portion K5 afelt washer M which is between said lugs and the rib member B. Anotherfelt washer M is arranged outside of the rib B and upon the iange 'B2'thereof which forms thebearing @on theJ f sleeve K. The thickness ofthese felt washers is such that when the sections and the strut membersare assembled the contact is metal members separated from each other.The felt bushing M2 within the sleeve K also holds the same frommetallic Contact with the spartube D. In the same manner the felticowasher M4 cushions the connection between the vertical struts and thesleeve member K.

The interposition of the felt washers between'lthe'strut members and thewing sectionsV will hold the adjacent edges of said members normallyspaced from each other.

The continuity of. the surface is preserved by vcovering these spaceswith tape, as indicated at N, which will produce an air seal v betweenthe section w-ithout interfering with shoulder thereon. Thus when anyiliring of the -spars produces an additional tension upon thebrace-members theend strut-memberis to move inward by compressing,-"outermost strut-member and bear against a.

` Assembling of the parts is accomplished by the spring P, which willpermit all of the intermediate strut-members to slide upon the spar andto equalize the stresses. At the same time the felt buffers between sections will be compressed to permit relative movement of said sectionsand the strutmembers.

Fuselaigc.

The fuselage comprises longerons Q, preferably formed of metallictubing, together with a series of ribs R sleeved upon these longeronsand of the peripheral c011- tour desired to be imparted to the outersurface of the fuselage. The ribs R are also sheet-metal stampingssimilar in construe# tion to the ribs B of thel wings and they areprovided with flanged apertures f or engaging the longerons, the flangesbeing bushed with .felt or similar material, as indicated at R. Atsuitable intervals crossstrut-members are arranged,these being attachedto the longerons by felt-hushed sleeves, the construction being similartov first engaging the rear ribs with the longerons while the latter arefree to be moved relatively to each other, and the progressively largerribs are then Vsuccessively engaged. The outer surface is formed in sec-,tions and for this purpose I preferably employ a thin board of suitablematerial, such as bakelite, this being capable of molding into the exact.form desired. f

The construction as thus far described is suficient to indicate thegeneral method of constructing and assembling .the elements of themachine. In brief, this consists, first, in the employment of thinmetallic stampings the edge contour of which imparts the desired form tothe wind-exposed surface; second, in securing the necessary mechanicalstrength by the use of strut-members associated with the ribs at..suitable intervals, but relieving the latter from stress; third, informing of said ribs andl strut-members unit sections which are slidablysleeved-upon longitudinal frame members and are movable thereonindependently of each other to impart iexibility; and fourth, in bracingbetween the strut-members.

As shown in Figs. 10 and 11l the rib menibers B have their edge 'flangesB provided with perforations 'B2 to permit of sewing the fabric thereto,and the web portionvof the rib is reinforced bybeading, as indicated atB3.. The ribs which are in the wing sections intermediate thestrut-members have their flanged apertures C'bushed with felt C so as toavoid direct contact with the metal of the spar tubes. Figs. 5 and 6,the brace connections L are anchored tothe strut members by engagingapertures in the adjacent ends of the nipples I and connecting tubes K2.These adjacent ends are preferably thickened in cross- As'indicated insection as indicated, and the apertures are i so fashioned as `to formround bearings for the brace cable, thereby avoiding danger of cutting.Intermediate the adjacent ends are felt washers M4 which absorb shocks.and vibration. This coupling connection for the brace securely holdsthe parts in position,

while at the same time permitting flexing movement of the frame. tionalsecuring devices may be provided for the nipples K', tubes K2,'nipple K3and tubes K4, such as the wire ties K7 passing through apertures in theabutting ends. The

If desired, addinipples and tubes are held in alinement by wind-exposedsurface, lcomprising a series` of complementary substantially .rigidsections and a frame on which said sections are mounted permittingindependent lateral movement thereof.

3. "In aircraft construction the combination with longitudinal framemembers, of a plurality of substantially rigid sections havingcomplementary wind-exposed surfacessaid sections being sleeved upon saidlongitudinal frame members and independently movable longitudinally ofthe frame.

4. In aircraft construction a plurality of substantially rigid sectionsforming complementary /portions of a continuous wind-exposed surface, aframe upon which said sections are mounted, and means for yieldablyholding said sections adjacent to each other.

5. In aircraft construction a plurality of substantially rigid sectionsforming complementary portions of a continuous wiid-exposed surface,means for yieldingly holding said sections adjacent to each other, andcushioning means intermediate said sections for absorbing shocks andvibrations.

Y dependent movement.

sleeved upon said frame members and independently movable thereon,cushioning means between said sections, and bracing means therebetweenpermitting of said in-v 8.l In aircraftJ construction a plurality ofsections forming complementary portions of a continuous wind-exposedsurface, each section comprising contour ribs and surfacing materialoverlying the same, a longitudinal frame member passing through alinedapertures in the ribs of said sections, and cushioning meansintermediate the adjacent.l end ribsof said sections.

9. In aircraft construction, a frame com- Erising longitudinal members,cross-struts etween said longitudinal members longitudinally movablysecured thereto, and bracing means between' said cross-struts permittingsaid independent movement of the cross-struts.

'10. In aircraft construction, a framecomprising longitudinal members, aseries of cross-struts between said longitudinal members longitudinallymovably secured thereto, bracing between said cross-'struts permittingmovement of the Asame on said longitudinal members, and resilient meansfor yieldably resisting movement.

11. In air craft construction, a series of substantially rigid sections,each comprising a pluralit of cross-connected contour ribsand surfa.i'ng material overlying the same,

ltudinal members, sai

longitudinal frame members passing through alined apertures in saidribs, cross-strutrnembers between certain of said'sections, and bracingybetween said 'crosslstrut-members. I

12. In aircraft construction, aplurality of sections formingcomplementary portions of a continuous wmd-exposed surface, eachof saidsections comprising cross-connected contour ribs and surfacing materialoverlying the same, longitudinal frame members passing throu h alinedapertures in said'ribs,

strut mem rs intermediate said sections lonsecured to said longi.strut-members having contour ribs and .covering material to formgitudinally adjustabl1 sections complementary to said first-mem' tionedsections, and bracing between said strut-members, passing throughapertures in the ribs of the intermediate sections. y

13. In aircraft construction, a plurality .of relativelymovable'sections forming complementary portions of a continuous'wind-exposed surface, each section comprising metallic stampingsforming contour ribs, crossconnections between said ribs and 'coverinrmaterial overlying sald ribs and secure thereto, said ribs having almedapertures therein, and longitudinal frame members engagin said alinedapertures.

14. n aircraft construction, a plurality of sections formingcomplementar portions of a continuous wind-exposed su ace cqmprisl ingmetallic stampings forming contour ribs having flanged edges and flangedalined apertures therethrough, covering material overlying said ribs andsecured 'to the anged edges thereof, bushings of cushioning material inthe vianged apertures ofsaid ribs, and longitudinal frame members en;gagino said bushed apertures.

15. n aircraft construction, a plurality of connected metallic elements,and a cushion of felt or similar material between adjacent elements forpreventing the'transmission of shocks and vibrations therebetween.

16. In aircraft construction, a wing comspar-members, each sectionconsisting of metallic stampings forming the contour ribs havingvperipheral flanges and anged apertures for engaging said sparmembers,cross# connections between said ribs, covering ma'- terial overlyingsaid ribs and secured to the peripheral flanges thereof, bushings of ycushioning material in the flanged apertures of certain of said ribs,buffer cushions intermediate lthe end ribs of-adjacent sections,

and flexible air sealing means between the peripheraledges of saidlast-mentioned ribs.

18'. In aircraftconstruction, a wing, comprising spar-members, aseriesof' alternately arranged wind-exposed surfacesections and strut-memberssleeved upon said spar-members, each of said wind surface sectionscomprising a plurality vf metallic stampings.

rming contour ribs, cross-connections between said ribs and coveringmaterial overlying said ribs and' peripherally secured. thereto, saidstrut-sections being provided with cross strut-members having sleeves atthe outer ends thereof and contour ribs with covering materialfsaidsleeves having bushin -of, cushioning material for engaging said spars,cushions4 intermediate said strut members and adjacent' sections, andbracing between saidstrut members passing through,I

-comprising longerons, a vseries of contour ribs formed of metallicstampings sleeved upon said longerons, bracing between said ribspermitting a limited independent movement thereof on said -longerons,and covering material overlying said ribs.

20. In aircraft construction, the combination with longitudinally alinedmembers forming a strut, of a brace connected to said members andforming a tie-connection therebetween. f

21; In aircraft construction, the combination with vabutting framemembers, of a brace connection threaded through apertures in theadjacent ends of said frame members forming a tie-connectiontherebetween and' being anchored thereby.

22. In aircraft construction, the combination with alined tubular framemembers, of a cushion member between the abutting ends, and a bracemember Vpassing through apertures in the adjacent ends ofi-said alinedmembers forming a tie-connection therebetween a'nd being anchoredthereby.

23. In aircraft construction, the combination with a longitudinal framemember, of a fashioned rib of sheet-metal sleeved upon said framemember, and a bushing -of felt forming a bearing for said rib member onsaid frame member.

24. In aircraft constructlon, the'combina- 'tion with complementarysections of a windexposed surface, of flanged ribs forming the adjacentends of said complementary sections, said anges being perforated,covering` material secured to said flanges by sewing through saidperforations, and a sealing strip bridging the joint between saidsections.

25. In aircraft construction, a bendable frame comprising a plurality ofsubstantially rigid elements and connections' between sald elementsyieldably -retaining the same in place.

' In 'testimony'whereof I aix my signature.

' EDMUND B. CARNS.

